Investigation of supersonic flutter of thick doubly curved sandwich panels with CNT reinforced facesheets using higher-order structural theory

Sankar, A.; Natarajan, Sundararajan; Zineb, Tarak Ben; Ganapathi, M.

doi:10.1016/j.compstruct.2015.02.047

Cited by 37 publications

(10 citation statements)

References 47 publications

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“…Because of the increasing number of new materials the different materials may be utilized as the facings and the core. Some of them used in the aircraft constructions and optimized with respect to the divergence or flutter behavior are given below: lattice sandwich panel [177], blade stiffened panel [178], rotated sandwich plates [179][180][181][182][183][184][185][186], PVC foam laminated wing [187][188][189][190], honeycomb with MR pockets [191], sandwich panels with CNT facesheets [192,193], FGM foam-Section 5.2.…”

Section: Sandwich Structuresmentioning

confidence: 99%

Optimal Design of Plated/Shell Structures under Flutter Constraints—A Literature Review

2019

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Aeroelastic optimization has become an indispensable component in the evaluation of divergence and flutter characteristics for plated/shell structures. The present paper intends to review the fundamental trends and dominant approaches in the optimal design of engineering constructions. A special attention is focused on the formulation of objective functions/functional and the definition of physical (material) variables, particularly in view of composite materials understood in the broader sense as not only multilayered laminates but also as sandwich structures, nanocomposites, functionally graded materials, and materials with piezoelectric actuators/sensors. Moreover, various original aspects of optimization problems of composite structures are demonstrated, discussed, and reviewed in depth.

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Section: Sandwich Structuresmentioning

confidence: 99%

Optimal Design of Plated/Shell Structures under Flutter Constraints—A Literature Review

2019

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“…The flutter characteristics of CNTRC sandwich DCPs have been examined in the work of Sankar et al. 50 Wang et al. 51 studied the vibration of CNTRC DCPs by utilizing a semi-analytical method.…”

Section: Introductionmentioning

confidence: 99%

Thermomechanical nonlinear stability of pressure-loaded functionally graded carbon nanotube-reinforced composite doubly curved panels with tangentially restrained edges

Trang

Tung

2019

Proceedings of the Institution of Mechanical Engineers, Part C:

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Geometrically nonlinear response of doubly curved panels reinforced by carbon nanotubes exposed to thermal environments and subjected to uniform external pressure are presented in this paper. Carbon nanotubes are reinforced into isotropic matrix through uniform and functionally graded distributions. Material properties of constituents are assumed to be temperature dependent, and effective elastic moduli of carbon nanotube-reinforced composite are determined according to an extended rule of mixture. Basic equations for carbon nanotube-reinforced composite doubly curved panels are established within the framework of first-order shear deformation theory. Analytical solutions are assumed, and Galerkin method is used to derive closed-form expressions of nonlinear load–deflection relation. Separate and combined effects of carbon nanotube distribution and volume fraction, elasticity of in-plane constraint, elevated temperature, initial imperfection, geometrical ratios and stiffness of elastic foundations on the nonlinear stability of nanocomposite doubly curved panels are analyzed through numerical examples.

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“…Lei et al [20,21] discussed FG-CNTRC cylindrical panel's free vibration as well as dynamic stability under static and periodic axial force via the Ritz method. Sankar et al [22] studied the supersonic flutter features of FG-CNTRC shells as well as double curved sandwich panels on the basis of higher-order structural theory by adopting QUAD-8 shear flexible shell factor. They considered the effect of the CNT's volume fraction, radius-to-thickness ratio, the aspect ratio, the shell thickness and core-to-face sheet thickness as well as temperature on the flutter boundaries.…”

Section: Introductionmentioning

confidence: 99%

Low-velocity impact response of nanotube-reinforced composite sandwich curved panels

Yang

et al. 2019

Sādhanā

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The low-velocity impact response of the sandwich curved panels with functionally graded carbonnanotube-reinforced composite (FG-CNTRC) surface and isotropic foam core is discussed in this paper. Five types of stacking arrangements including uniform distribution of FG-CNTRC considering thermal environment were analysed. Using the Hertz contact law and rule of mixture model as well as the Kármán-type equations, the nonlinear formulations were built and solved by the two-step perturbation method. The carbon nanotubes' volume fraction, the structure size, the original impact velocity, temperature, relative thickness and the influence of gradient forms on the panels' impact behaviours were analysed. The outcomes show that the stiffness of the non-contact surface has large influence on contact response and various types of FG-CNTRC can be used for different operating conditions providing stiffness or cushion performance.

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Investigation of supersonic flutter of thick doubly curved sandwich panels with CNT reinforced facesheets using higher-order structural theory

Cited by 37 publications

References 47 publications

Optimal Design of Plated/Shell Structures under Flutter Constraints—A Literature Review

Optimal Design of Plated/Shell Structures under Flutter Constraints—A Literature Review

Thermomechanical nonlinear stability of pressure-loaded functionally graded carbon nanotube-reinforced composite doubly curved panels with tangentially restrained edges

Low-velocity impact response of nanotube-reinforced composite sandwich curved panels

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